TURBOMACHINE POLYSPHERICAL HUB FOR VARIABLE PITCH BLADES

Abstract

The present invention concerns a turbomachine hub, intended to be mounted so as to be able to rotate about a longitudinal axis (X) of the turbomachine, the hub comprising a main body (1) arranged around the longitudinal axis (X), an outer surface of which has a plurality of recesses; a plurality of platforms (3) comprising an outer surface delimited by a circular outer edge of radius r, each platform (3) being arranged in a corresponding recess of the plurality of recesses of the main body (1), and intended to receive a variable pitch blade (2), the pitch of which is variable according to a pitch change axis (Z), the platform (3) being centred and able to rotate about the pitch change axis (Z); characterised in that, for each platform, at least one part of the outer surface of the platform (3) and the main body (1) of the hub comprises a curvature defined by a same sphere portion of radius R and centre C, the at least one part being situated at the outer edge of the platform (3), in a junction zone between the platform (3) and the main body of the hub (1), the centre C of the sphere being situated on the pitch change axis (Z) outside a hemispherical zone delimited between the longitudinal axis (X) and the outer surface of the platform (3).

Claims

1. A turbomachine hub intended to be mounted in rotation along a longitudinal axis (X) of a turbomachine (10), the turbomachine hub comprising a main body (1) disposed around the longitudinal axis (X), of which an outer surface has a plurality of housings; a plurality of platforms (3) comprising an outer surface delimited by a circular outer edge of radius r, each platform (3) being disposed in a corresponding housing of the plurality of housings of the main body (1), and intended to receive a variable pitch blade (2) according to a pitch change axis (Z), the platform (3) being centered and movable in rotation along the pitch change axis (Z); wherein, for each platform, at least part of the outer surface of the platform (3) and of the main body (1) of the turbomachine hub comprises a curvature defined by the same spherical portion of radius R and center C, the at least one part being situated at the outer edge of the platform (3), in a junction zone of the platform (3) and of the main body of the turbomachine hub (1), the center C of the sphere being situated on the pitch change axis (Z) outside a hemispherical zone delimited between the longitudinal axis (X) and the outer surface of the platform (3).

2. Turbomachine hub according to claim 1, wherein the outer surface of the platform (3) is entirely defined by the spherical portion of radius R and center C.

3. Turbomachine hub according to claim 1, wherein the junction zone is defined by a projection of the junction zone into a plane orthogonal to the pitch change axis (Z), the projection being a ring centered on the pitch change axis (Z) and delimited between a circle with inner radius ri less than the radius r of the outer edge of the platform (3), and a circle with outer radius re greater than the radius r of the outer edge of the platform (3).

4. Turbomachine hub according to claim 3, wherein the outer surface of each platform (3) comprises a central part having a curvature opposite to the curvature of the outer surface in the junction zone, a projection of the central part in the plane orthogonal to the pitch change axis (Z) being delimited by the circle of inner radius ri.

5. Turbomachine hub according to claim 1, wherein the center C of the sphere defining the outer surface of each platform (3) is situated at the intersection of the pitch change axis (Z) and of the longitudinal axis (X).

6. Turbomachine hub according to claim 1, wherein the main body of the turbomachine hub (1) comprises a plurality of intermediate zones situated between two junction zones with adjacent platforms (3), each intermediate zone having an outer surface having a curvature opposite to the curvature of the outer surface of the main body (1) in the junction zone.

7. A turbomachine assembly comprising a turbomachine hub according to claim 1 and a plurality of variable pitch blades (2) configured to be connected to the main body of the turbomachine hub (1) by means of the plurality of platforms (3).

8. Assembly according to claim 7, wherein each platform (3) of the plurality of platforms (3) is made in one piece with the corresponding blade (2) of the plurality of blades (2).

9. Assembly according to claim 7, wherein each platform (3) comprises at least two distinct parts, intended to surround a root part of the corresponding blade (2).

10. Assembly according to claim 7, wherein the outer surface of each platform (3) is complementary to the shape of the corresponding blade (2), so that the platform (3) is in contact with the blade (2) from the leading edge of the blade to the trailing edge of the blade (2), and is also in contact with the suction side and the pressure side of the blade (2).

11. A turbomachine with a shrouded (10) or unshrouded fan, comprising an assembly according to claim 7.

Description

DESCRIPTION OF THE FIGURES

[0041] Other features, objects and advantages of the invention will be revealed by the description that follows, which is purely illustrative and not limiting, and which must be read with reference to the appended drawings in which:

[0042] FIG. 1 illustrates schematically a section view of a turbomachine with a shrouded fan.

[0043] FIG. 2 illustrates schematically a front and 90° rotated view of a turbomachine assembly comprising a hub according to one exemplary embodiment.

[0044] FIG. 3A illustrates schematically a side view of a variable pitch blade connected to a hub by a platform according to a first exemplary embodiment.

[0045] FIG. 3B illustrates schematically a side view of a variable pitch blade connected to a hub by a platform according to a second exemplary embodiment.

[0046] FIG. 3C illustrates schematically a side view of a variable pitch blade connected to a hub by a platform according to a second exemplary embodiment.

[0047] FIG. 4 illustrates schematically a top view of a variable pitch blade connected to a hub by a platform.

[0048] FIG. 5 illustrates schematically a side view of a variable pitch blade connected to a polyspherical hub by a platform.

[0049] FIG. 6A illustrates schematically a front view of a turbomachine assembly comprising a polyspherical hub and a plurality of variable pitch blades according to a first exemplary embodiment.

[0050] FIG. 6B illustrates schematically a front view of a turbomachine assembly comprising a polyspherical hub and a plurality of variable pitch blades according to a second exemplary embodiment.

[0051] FIG. 7 illustrates schematically a top view of the variable pitch blade of FIG. 4, in two different pitch positions.

[0052] FIG. 8 illustrates schematically a side view and a top view of the variable pitch blade connected to the polyspherical hub of FIG. 5.

[0053] FIG. 9 illustrates schematically a side view of the variable pitch blade connected to the polyspherical hub in another exemplary embodiment.

[0054] In all the figures, similar elements bear identical reference symbols.

DETAILED DESCRIPTION OF THE INVENTION

[0055] Considered is a propulsion system for aircraft of the turbomachine type, comprising an engine shaft mounted in rotation along a longitudinal axis of rotation X, corresponding to an axis of symmetry of the turbomachine.

[0056] As previously explained, the turbomachine can have, according to a first exemplary embodiment, a shrouded fan architecture, or according to a second exemplary embodiment, an open rotor architecture.

[0057] FIG. 1 illustrates the first example of turbomachine 10 architecture in which the solution to the technical problem posed can be used. The turbomachine 10 has an architecture with a fan with an ultra-high bypass ratio or UHBR. It comprises a compact nacelle 20, particularly with a reduced length. In particular, the nacelle 20 with a reduced length integrates an upstream air inlet and a secondary nozzle downstream of the fan with a reduced length. This nacelle does not integrate a thrust reverser mechanism. It has as its main functions to provide the aerodynamic fairing of the turbomachine 10 and to retain the fan blades 2 and is only dimensioned for this purpose.

[0058] A structure 30 defines the outside of a primary stream, a secondary stream being defined between the nacelle and the outside of this structure 30. The structure 30 comprises an inter-compressor casing 31, disposed between a low-pressure compressor 12 and a high-pressure compressor, an inter-turbine casing 32, disposed between a low-pressure turbine 13 and a high-pressure turbine, as well as an exhaust casing 33. A straightener 11 is interposed between the nacelle 20 and the structure 30 and allows retaining said nacelle 20.

[0059] In one possible exemplary embodiment, a part of the nacelle 20 can be made common with an already existing surface on the aircraft, such as for example the pressure side of the airfoil. Regardless of the architecture considered, the turbomachine 10 comprises parts mounted in rotation on the axis of rotation X, called the rotor. The rotor comprises a hub driving in rotation around the axis X a plurality of variable geometrical pitch blades 2. A mechanism 4 allows the rotation of each of the blades 2 around a substantially radial axis Z also called the stacking axis Z or pitch change axis Z. It is specified that each blade has its own pitch change axis. What is meant by “substantially radial” is that the axis of rotation Z of the blade 2 is orthogonal to the longitudinal axis of rotation X, or can have an angular offset less than a few degrees with an axis orthogonal to the longitudinal axis of rotation X.

[0060] According to conventional usage of the following terms, each blade 2 has a leading edge, facing a flow of air passing through the turbomachine 10, and an opposite trailing edge in the longitudinal direction X, the straight-line segment connecting the trailing edge to the leading edge being defined as the chord considered at a radial position selected radially on the radial axis Z. The blade 2 comprises a face called the suction side extending radially, at which a reduced pressure occurs, and an opposite face called the pressure side, at which an increased pressure occurs.

[0061] What is meant by geometric pitch is the angle formed by the chord of the profile of the blade 2 and the plane of rotation of the rotor, defined as a plane orthogonal to the axis of rotation X of the turbomachine 10.

[0062] Hereafter, what will be meant by “outer surface” is a surface that is external with regard to the longitudinal axis of rotation X, particularly along which the air flows can circulate.

[0063] Conventionally, the variable pitch blades 2 are situated above the hub with a substantially cylindrical shape around the axis of rotation X. The blades 2 can typically be evenly distributed on an outer surface of the hub 1, along its circumference.

[0064] FIG. 2 illustrates schematically an exemplary embodiment of the hub in the plane of rotation of the rotor (O,{right arrow over (Y)},{right arrow over (Z)}), and in a plane (O,{right arrow over (X)},{right arrow over (Z)}) tangent to the axis of rotation X.

[0065] The hub comprises a main body 1 disposed around the longitudinal axis X. The main body of the hub 1 is fixed in the rotating reference frame of the engine shaft, i.e. it is intended to be driven in rotation by the engine shaft around the longitudinal axis of rotation X.

[0066] The main body of the hub 1 generally consists of a single piece. The main body of the hub 1 comprises a plurality of housings. Preferably, the housings are distributed over the outer circumference of the hub 1 concentrically with the longitudinal axis of rotation X. Each housing can have a substantially circular shape, i.e. have an inner edge delimited by a circle of radius r.

[0067] The hub comprises a plurality of platforms (3), each disposed in a corresponding housing of the plurality of housings of the main body 1.

[0068] According to the example of FIG. 2, it will be understood that each platform (3) is intended to receive a corresponding variable pitch blade (2), and is movable in rotation along a specific radial axis (Z, Z′). Thus, each platform (3) is intended to be secured to a root of the corresponding variable pitch blade (2), and to turn with the blade (2) depending on the desired pitch.

[0069] In one exemplary embodiment, each platform (3) can be connected fixedly to a mechanism 4 for actuating the variable pitch (“pitch control mechanism” or PCM), connected by a pivot link to the main body of the hub 1.

[0070] FIG. 4 illustrates schematically a top view of an exemplary embodiment of the platform 3, in a plane orthogonal to the pitch change axis Z. Each platform 3 comprises an outer surface delimited by a circular outer edge 3a of radius r. The circular outer edge of radius r forms a junction between the main body of the hub 1 and the platform 3.

[0071] The platform 3 comprises a perforation delimited at least by an inner edge 3b of the platform, intended to be in direct contact with the root of the blade 2, or alternatively to be in contact with the root of the blade 2 by means of a gasket. Advantageously, the gasket, preferably made of elastomeric material, can appear in the form of a strand glued or assembled to the platform, with a width equivalent to the clearance existing between the blade root and the platform.

[0072] It is not intended for each platform 3 to be fixed in the rotating frame of reference of the engine shaft, but to be mounted in rotation relative to the pitch change axis Z. Each platform 3 is therefore mounted movable in rotation relative to the pitch change axis Z, and is centered on the pitch change axis Z.

[0073] The center of the circle of radius r delimiting the outer edge 3a in the plane orthogonal to the pitch change axis Z is disposed on the pitch change axis Z, as illustrated in FIG. 4. This advantageously allows limiting the clearance between the platform 3 and the main body of the hub 1, regardless of the pitch of the blade 2.

[0074] As will be detailed hereafter, each platform 3 is designed to provide geometrical continuity between the blade 2 and the main body of the hub 1, over the entire pitch range of the blade 2, while guaranteeing the aerodynamic performance of the hub. Preferably, the shape of the outer surface of each platform 3 and of the main body of the hub 1 allows limiting the perturbations of the boundary layer at the platform 3, and more generally limiting useless perturbations of the air flow.

[0075] In order to retain the continuity of the hub at the intersection between the platform 3 and the main body of the hub 2, i.e. along the outer edge 3a of the platform 3, the platforms 3 and the main body of the hub 1 are polyspherical.

[0076] As illustrated schematically in FIG. 5, what is meant by polyspherical is that at least a part of the outer surface of the platform 3 and of the main body of the hub 1 comprises a curvature defined by the same spherical portion of radius R and with center C, of which the intersection with the plane of FIG. 5 is shown in a thin dotted line. The part of the outer surface of the hub is situated at the outer edge 3a of each platform 3, in a junction zone between the platform 3 and the main body of the hub 1. Here it is specified that the curvature is the inverse of the radius and is therefore inversely proportional. A small radius implies strong curvature.

[0077] For each platform 3, the center C of the sphere is situated on the pitch change axis Z, outside a hemispherical zone delimited between the longitudinal axis (X) and the outer surface of the platform 3.

[0078] Thus, the circular outer edge 3a corresponds to an apparent contour of the sphere with center C and radius R, i.e. the circle corresponding to the intersection of the sphere with the plane orthogonal to the pitch change axis Z illustrated in FIG. 4. The junction zone extends on the sphere on either side of this apparent contour. There is continuity of the outer surface of the platform 2 with the outer surface of the main body of the hub 1 in the junction zone, regardless of the pitch of the platform 2.

[0079] The radius R can be imposed by a minimum or maximum axial position of the platform 3. As illustrated in particular in FIG. 5, the radius R can be different from the radius of the hub Rm at this axial position.

[0080] FIG. 6A illustrates a first exemplary embodiment, in which the center C defining the sphere delimiting the junction zone can be situated below the hemispherical zone delimited between the longitudinal axis (X) and the outer surface of the platform 3. As illustrated in the plane (O,Y,Z), the center C is located on the axis Z, below the intersection O between the longitudinal axis of rotation X and the pitch change axis Z. The circle with center O in dashed lines shows the substantially cylindrical cross section of the hub. The construction lines and the circle with center C in thin dotted lines illustrate the cross section of the portion of the sphere defining a part of the outer surface of the platform 3 and of the main body of the hub 1 in the junction zone.

[0081] In the first exemplary embodiment, each platform (3, 3′) has a substantially convex shape. In the reference frame (O,{right arrow over (Y)},{right arrow over (Z)}), {right arrow over (OC)}=−∥{right arrow over (OC)}∥{right arrow over (z)}. In the first example illustrated, 0<∥{right arrow over (OC)}∥<Rm however, the center C can be outside the circle with center O, so that ∥{right arrow over (OC)}∥≥Rm.

[0082] In a second exemplary embodiment (not illustrated), corresponding to a particular case of the first exemplary embodiment, the center C of the sphere defining in part the outer surface of the platform 3 is situated at the intersection O between the longitudinal axis of rotation X and the pitch change axis X. A spherical hub is then referred to.

[0083] As for spherical, it is considered that at least part of the outer surface of each platform 3 and the outer surface of the main body of the hub 1, in the junction zone at the outer edge of the platform 3a, are defined by a spherical portion with center O.

[0084] In this particular case, the centers of each sphere defining the outer surface of a platform (3, 3′) are congruent. The radius R of the sphere is imposed by the position of the intersection between the axis of rotation of the hub (longitudinal axis X) and the axis of rotation of the platform 3 (pitch change axis Z).

[0085] Preferably, the assembly of the main body of the hub 1 and of the platforms 3 follows the definition of the spherical stream at the blades 2. The platforms 3 can then be created by cutting out the hub 1 around each pitch change axis Z.

[0086] The second exemplary embodiment has the advantage of retaining a hub with cylindrical symmetry while limiting curvatures. In fact, for each axial position of the blading zone, this solution allows obtaining circular cross sections of the hub and thus limiting curvature in the azimuthal direction. A low curvature allows reducing aerodynamic perturbations at the blade 2 root, and avoiding in particular accelerations of an air flow in these junction zones. Propulsive efficiency losses are thus reduced.

[0087] FIG. 6B illustrates a third exemplary embodiment, in which the center C defining the sphere of the platform 3 can be situated above the hemispherical zone delimited between the longitudinal axis (X) and the outer surface of the platform 3, on the pitch change axis Z. The center C is situated above the circle of radius Rm delimiting the substantially circular shape of the hub, shown in dashed lines. The construction lines and the circle with center C in thin dotted lines illustrate the cross section of the portion of the spherical portion defining a part of the outer surface of the platform 3 and of the hub 1.

[0088] In the third exemplary embodiment, each platform 3 has a substantially concave shape. Within the frame of reference (O,{right arrow over (Y)},{right arrow over (Z)}), {right arrow over (OC)}=∥{right arrow over (OC)}∥{right arrow over (z)} and ∥{right arrow over (OC)}∥>Rm.

[0089] Thus, at least a portion of each platform and of the main body of the hub 1 at the outer edge 3a in the junction zone is defined according to a sphere of radius R and center C, the center C being disposed on the pitch change axis Z of the platform 3, outside the hemisphere with center O and radius Rm, defined in the space{x.sup.2+y.sup.2+z.sup.2=Rm.sup.2|z>0}.

[0090] This allows advantageously limiting the curvatures of the outer surface of the platform 3 and of the main body of the hub 1. In fact, if in the frame of reference (O,{right arrow over (Y)},{right arrow over (Z)}), {right arrow over (OC)}=OC {right arrow over (z)}, and 0<OC<Rm, the concavity or the convexity of the outer surface of the platform 3 will be large, which can cause aerodynamic perturbations of an air flow passing through the turbomachine 10m and consequently cause a loss of propulsive efficiency.

[0091] This definition allows that a point situated on the outer edge 3a of each platform 3 will always be at the same radius R on this portion of the sphere despite the pitch rotation of the associated blade 2 around the axis Z.

[0092] FIG. 7 illustrates schematically the two angular positions or different pitches of the blade 2 associated with the platform 3 relative to the main body of the hub 1, in the plane orthogonal to the pitch change axis Z of FIG. 4.

[0093] The Cartesian coordinates of any point P situated on the outer edge of the platform of the pitch change axis Z are denoted (Xi, Yi, Zi), in the direct orthogonal frame of reference (O, {right arrow over (X)}, {right arrow over (Y)}, {right arrow over (Z)}). The coordinates of the point P prior to pitch variation are denoted (X.sub.1,Y.sub.1,Z.sub.1), and (X.sub.2,Y.sub.2,Z.sub.2) the coordinates of the point P′, corresponding to the transformation of the point P by a rotation around the pitch change axis Z, after variation of the pitch.

[0094] During a pitch variation, the platform 3 performs a rotation around the axis Z, so that at any point of the outer edge 3a of the platform 3 forming a circle centered on the pitch change axis Z, the coordinate along the pitch change axis Z does not vary. Therefore, Z.sub.1=Z.sub.2.

[0095] In the plane (O,{right arrow over (X)},{right arrow over (Y)}) illustrated in FIG. 7, the point P performs a rotation around the pitch change axis Z so that X.sub.1.sup.2+Y.sub.1.sup.2=X.sub.2.sup.2+Y.sub.2.sup.2.

[0096] Thus the radius R′ relative to the center C of the sphere from the point P′ after rotation will be identical to the radius R. In fact, R′=√{square root over (X.sub.2.sup.2+Y.sub.2.sup.2+Z.sub.2.sup.2)}=√{square root over (X.sub.1.sup.2+Y.sub.1.sup.2+Z.sub.1.sup.2)}. The radius R′ will therefore not have changed and will be identical to that of the main body of the hub 1 at this position, which allows ensuring the continuity of the outer surface of the hub, therefore of the stream, and not creating steps.

[0097] In an exemplary embodiment of the platform 3, shown for example in FIGS. 5 and 6, the outer surface is entirely defined by the spherical portion of radius R and center C.

[0098] In order to ensure the continuity of the outer surface of the hub, it is however not necessary that the entire outer surface of each platform 3 be defined by the sphere of center C and radius R.

[0099] Likewise, it is not necessary that the entire outer surface of the main body of the hub 1 between the platforms (3, 3′) be defined by a sphere.

[0100] In one exemplary embodiment, the main body of the hub 1 can comprise a plurality of intermediate zones situated between two junction zones with the adjacent platforms 3, each intermediate zone having an outer surface having a curvature opposite to the curvature of the outer surface of the main body 1 in the junction zone.

[0101] Preferably, only a portion of each platform 3 and of the hub 1 is spherical.

[0102] As illustrated schematically in FIG. 8, it is possible to define two limit radii: a first inner radius ri and a second outer radius re. The inner ri and outer re radii delimit the junction zone in which the outer surface of the main body 1 and of the platform 3 must at a minimum be defined by the sphere with center C. This junction zone allows guaranteeing a continuity of the stream at the outer edge 3a delimiting the interface between the platform 3 and the main body of the hub 1.

[0103] FIG. 8 illustrates in particular a top view of the platform 3, in the plane orthogonal to the pitch change axis Z of FIG. 5. This view illustrates the projection of the junction zone into this plane orthogonal to the pitch change axis (Z), and allows simply defining the junction zone. The radius of the platform in the plane (O,{right arrow over (X)},{right arrow over (Y)}) is denoted r, so that ri<r<re. The projection into this plane is, in this example, a ring centered on the pitch change axis (Z) and delimited between a circle with inner radius ri less than the radius r of the outer edge of the platform 3, and a circle with outer radius re greater than the radius r of the outer edge of the platform 3.

[0104] The spherical portion of the main body of the hub 1 and of the platform 3 must allow the continuity, at least in curvature, of the hub in the zone comprised between the radii ri and re.

[0105] In a preferred exemplary embodiment, the outer surface of each platform 3 comprises a central part having a curvature opposite to the curvature of the outer surface of the junction zone.

[0106] In order to guarantee continuity, the projection of the central part into the plane orthogonal to the pitch change axis (Z) can be delimited by the circle with inner radius ri.

[0107] FIG. 9 illustrates an exemplary embodiment of this type, in which the outer surface of the platform 3 inside the circle defined by ri has a substantially concave shape, while the junction zone between ri and re is convex.

[0108] It is advantageous to adapt the geometry of this inner zone to manage the flow speed of a blade 2 root air flow. This has no consequence for the continuity of curvature of the platform 3—main body of the hub 1 interface.

[0109] Preferably, the geometry of the outer surface of the main body of the hub 1 outside the circle delimited by re and centered on the pitch change axis Z can be adapted, so as to manage the flow speed of a blade 2 root air flow.

[0110] It is for example possible to increase the passage cross section at the blade 2 root by hollowing the main body of the hub 1 between two successive platforms 3. This advantageously allows reducing the relative Mach number on the profiles, which is beneficial for the performance of the turbomachine.

[0111] Preferably, the geometry of the main body of the hub 1 outside the circle delimited by re and centered on the pitch change axis Z can be adapted, by increasing the radius Rm in proximity to the pitch change axis Z. This allows facilitating the integration of the pitch change mechanism 4 (PCM).

[0112] In the example illustrated in FIG. 9, the main body of the hub 1 comprises a zone outside the junction zone with a concave shape, while the junction zone is convex.

[0113] Thus the technical solution proposed allows eliminating the step existing in the prior art between the platform 3 and the main body of the hub 1, while guaranteeing the continuity of curvature of the stream during the pitch rotation, therefore regardless of the pitch of the blade 2. It is thus possible to guarantee good aerodynamic performance and to improve the propulsive efficiency of the turbomachine 10.

[0114] According to one aspect, a turbomachine assembly is considered comprising a polyspherical or spherical hub as previously described, and a plurality of variable pitch blades 2 configured to be connected to the main body of the hub 1 by means of the plurality of platforms 3.

[0115] FIGS. 3A, 3B and 3C illustrate schematically different exemplary embodiments of the blade 2 with the platform 3.

[0116] In one exemplary embodiment illustrated in FIG. 3A, the platform 3 can be an extension of the root of the blade 2, i.e. the platform 3 and the associated blade 2 are made in a single piece. An “integrated” platform is then referred to.

[0117] In an alternative exemplary embodiment, the platform 3 can comprise at least one distinct part of the blade 2 and be installed around the blade 2. An “applied” platform is then referred to.

[0118] Preferably, the applied platform 3 can be formed from at least two distinct parts intended to surround a root part of the corresponding blade 2.

[0119] For example, the platform 3 can comprise a first part intended to be in contact with the pressure side of the blade 2 and a second part intended to be in contact with the suction side of the blade 2. This advantageously allows facilitating the assembly of the platform 3 into the corresponding orifice of the hub 1.

[0120] According to one exemplary embodiment of the platform 3 illustrated schematically in FIG. 3B, the root of the blade 2 is configured to extend below the platform 3, and to continue under the hub 1 in the form of an extrusion. In this exemplary embodiment, the platform can surround the blade without radial clearance, which is beneficial from the aerodynamic standpoint, but this constrains the platform to have a radius r greater than or equal to half the chord of the profile of the blade 2 at the root.

[0121] Generally, the platform 3 can have a radius r less than half the chord of the profile of the blade 2 at the root, so that there exists a radial clearance between the platform 3 and the trailing edge and leading edge points of the blade 2. This could however induce a greater perturbation of the air flow.

[0122] According to a preferred exemplary embodiment illustrated in FIG. 3C, the outer surface of the platform 3 is complementary with the shape of the blade 2, so that the platform is in contact with the blade 2 from the leading edge of the blade 2 to the trailing edge, and is also in contact with the suction side and the pressure side. This advantageously allows avoiding the creation of radial clearance, and guaranteeing the continuity of the shape between the blade 2 and the platform 3. In this example, illustrated in FIG. 3C, a particular case is involved of that illustrated in FIG. 3B, in which r=chord/2.

[0123] As explained previously, an assembly of this type can be advantageously used for a turbomachine with a shrouded fan or for a turbomachine with an unshrouded fan, of the “open rotor” type.