FR3070427A1 - INSERT FOR FIXING A COMPONENT ON A TURBOMACHINE SUPPORT - Google Patents

Abstract

Insert (100) for attaching a component (32) to a turbomachine support (26), the insert (100) being configured to be assembled to the component (32) and the carrier (26) and comprising a configured socket to receive a fastener (40), and at least one fin projecting transversely of the sleeve.

Description

FIELD OF THE INVENTION The present disclosure relates to an insert for fixing a component on a support. Such an insert can in particular be used for fixing a turbomachine blade made of composite material on a metal casing, or more generally as a fixing interface for the mutual fixing of a component and of a turbomachine support possibly made of materials different.

TECHNOLOGICAL BACKGROUND [0002] In fields such as aeronautics, lightening of devices is a constant concern of manufacturers. For example, in aircraft engines, it is known to replace certain metal blades with blades made of composite material, which have the advantage of being lighter.

However, the composite vanes break more easily than the metal vanes when they are subjected to imposed deformations. However, the certification authorities require engines to reasonably resist certain incidents such as the loss of a fan blade or the ingestion of a medium-sized bird. In particular, these incidents induce displacements of the engine casing which strongly urge the outlet guide vanes (in English Outiet Guide Vanes, hereinafter OGV) located in the cooling stream, just downstream of the fan.

Thus, at present, it is not possible to replace conventional metallic OGVs with composite blades because the latter would not withstand the imposed displacements occurring during this type of incident sufficiently.

There is therefore a need for a new system making it possible to generalize the use of components made of composite materials in a turbomachine.

PRESENTATION OF THE INVENTION To this end, the present disclosure relates to an insert for fixing a component on a turbomachine support, the insert being configured to be assembled to the component and to the support and comprising a socket configured for receiving a fixing member, and at least one fin projecting transversely from the socket.

[0007] A turbomachine support is a support that can be used in a turbomachine. Furthermore, within the meaning of the present description, the insert, or even the sleeve, extends generally along an axis. The axial direction corresponds to the direction of the tax of the insert and a radial direction is a direction perpendicular to this axis and intersecting this axis. Likewise, an axial plane is a plane containing the tip of the insert and a radial or transverse plane is a plane perpendicular to this axis. A circumference is understood as a circle belonging to a radial plane and whose center belongs to the axis of the insert. A tangential or circumferential direction is a direction tangent to a circumference; it is perpendicular to the axis of the insert but does not pass through the axis.

Unless otherwise specified, the inner and outer adjectives are used with reference to a radial direction so that the inner part of an element is, in a radial direction, closer to the axis of the insert than the part exterior of the same element.

The fin may be a portion of the circumferentially delimited collar; the fin does not go completely around the socket. The fin can take the general shape of a plate or sheet, flat or curved. The fin can extend substantially in a transverse plane.

The socket can be configured to receive a fixing member. In these cases, the fixing member may be integral with the socket and / or formed permanently with the socket. The fixing member can also be separated from the socket. The fixing member, possibly integrated into the socket, allows the component to be fixed to the support via the insert and more particularly via the socket.

The insert can be assembled directly or indirectly to the component and to the support. According to one example, the insert can be assembled directly to the component, for example embedded in the component, or indirectly assembled to the support, for example by means of the fixing member. According to a variant, the component and the support can be reversed in the previous example.

Thanks to the fact that the insert comprises a bushing and a fin projecting transversely from the bushing, the insert can serve as a fixing intermediary between the component and the support. The fin makes it possible to strengthen the connection between the component and the support in the vicinity of the socket, to compensate for the possible rupture of the component or of the support by a deformation of the fin and to move the critical zone of the socket towards the end. distal of the fin. Thus, thanks to the insert, the component better resists displacements which are imposed on it by the support and vice versa.

In the case of an aircraft turbomachine, such an insert, assembled to an OGV made of composite material, is therefore able to ensure the resistance of the OGV in response to the displacements imposed by the casing on which the 'OGV is fixed, said casing forming a turbomachine support.

In some embodiments, the sleeve comprises at least two sections substantially of symmetry of revolution and of different external diameters, the sections being assembled together in an axial direction of the sleeve. The axis of symmetry of the two sections is preferably the axis of the sleeve, preferably coincident with the axis of the insert. This results in better axial integration of the insert into the component and / or the support.

In some embodiments, the sleeve includes an internal threaded part and the fixing member comprises a threaded rod. Thus, the internal threaded part is configured to cooperate with a threaded rod of the fixing member. The attachment between the component and the support can therefore be removed. Alternatively, the fixing member can form a non-removable fixing and can be, for example, a rivet, a pin, a ratchet pawl, etc.

In some embodiments, the fin has a decreasing axial thickness from the sleeve towards the distal end of the fin. This makes it possible to provide an appropriate transition between the structure of the insert and the structure of the component. According to one example, said thickness may decrease in stages: in this case, the fin may have at least two fin sections each of constant axial thickness, the thickness of each fin section being strictly less than the thickness of the fin section adjacent to the side of the sleeve.

In some embodiments, in cross section, the fin extends circumferentially between two tangents of the sleeve parallel to each other. Thus, the transverse size of the sleeve is limited and the sleeve can be judiciously oriented so that the fin only has an effect in certain directions. Optionally, the fin can extend continuously between said two tangents. Optionally, the fin can occupy the entire interval between said two tangents.

In some embodiments, the insert is made of metal. This term includes metal alloys.

The present disclosure also relates to an assembly for a turbomachine comprising a component and an insert as previously described, the insert being assembled to the component.

In some embodiments, the component is made of composite material having a fibrous reinforcement in the form of folds, and the fin is held, on either side in an axial direction, between some of said folds. Thus, the insert is integrated into the component and the fin allows good anchoring of the insert in the component. This results in a better distribution of forces within the component in the event of an incident, therefore in a reduction in the stresses to which the component is subjected.

In some embodiments, the insert is provided on one side of the component and the fin extends to an opposite side of the component. The fin is therefore directed towards the interior of the component and makes it possible to better accommodate the displacements between the support, where the displacements are imposed, and the interior of the component which as such can poorly resist the imposed displacements.

In some embodiments, the component is a turbomachine blade. The component may be an OGV. Thus, according to one example, the insert can form a fixing interface between an OGV made of composite material and a metal casing, the insert accommodating, by its deformation and in particular the deformation of the fin, the displacements imposed by the casing which the OGV would not otherwise resist.

In some embodiments, the blade comprises at least one platform and a blade extending from the platform, and the insert is housed in the platform. Thus, the attachment of the insert to the turbomachine support, generally a casing, is easy.

The platform is preferably made in one piece with the blade. More particularly, when the fin is held, on either side in an axial direction, between certain folds of the composite blade, said folds preferably extend continuously from the platform to the blade. Thus, the distribution of stresses in the dawn is optimal.

Alternatively, the component can be a protective panel, for example made of composite material, for example an acoustic panel.

The present disclosure also relates to an assembly comprising a turbomachine support and an insert as previously described, assembled to the support. This assembly may have all or some of the characteristics described above with respect to the assembly comprising the component and the insert, mutatis mutandis.

BRIEF DESCRIPTION OF THE DRAWINGS The invention and its advantages will be better understood on reading the detailed description which follows, of embodiments of the invention given by way of nonlimiting examples. This description refers to the accompanying drawings, in which:

- Figure 1 shows a schematic section of a turbomachine;

- Figure 2 shows, in axial section of the turbomachine, an OGV fixed to a housing according to one embodiment;

- Figure 3 is an axial sectional view of a first insert according to one embodiment;

- Figure 4 is a top view of the first insert, in direction IV of Figure 3;

- Figure 5 is a detail view of the area V of Figure 2 and shows, in axial section, the integration of the first insert;

- Figure 6 schematically illustrates an example of deformation of the assembly of Figure 2, in zone V;

- Figure 7 is an axial sectional view of a second insert according to one embodiment;

- Figure 8 is a bottom view of the second insert, in the direction VIII of Figure 7;

- Figure 9 is a detail view of the area IX of Figure 2 and shows, in axial section, the integration of the second insert;

- Figures 10A-10D schematically illustrate different examples of deformation of the assembly of Figure 2, in zone IX;

DETAILED DESCRIPTION OF THE INVENTION The overall architecture of a turbomachine which can incorporate an embodiment of the invention will be described with reference to FIG. 1, which presents an axial section of a turbomachine 12. Upstream , the turbomachine 12 comprises a fan 14 for the admission of air. At the outlet of the blower 14, the air flow separates in two. A first part of the air flow is sent to a low pressure compressor 16 then a high pressure compressor 18. This first part of the air flow is then injected into a combustion chamber 20, at the outlet of which it drives a turbine. 22. A second part of the air flow, at the outlet of the blower 14, is sent, between an external casing 24 and an internal casing 26, to a rectifier comprising vanes 30 to be rectified and then mixed with the gases leaving the turbine 22. The second part of the air flow can be used, in part, for cooling the turbomachine 12.

As illustrated in more detail in FIG. 2, a stator vane 30, here an output guide vane or OGV 30, forming an example of a component within the meaning of the present description, is fixed on the external casing 24 and on the internal casing 26, each of these casings forming an example of a turbomachine support, or more simply a support, within the meaning of the present description.

In this case, the OGV 30 comprises at least one platform, here two platforms 32, 34, and a blade 36 extending between the two platforms. The platforms 32, 34 delimit, in a radial direction of the turbomachine, an air passage called cooling or secondary stream, as opposed to the primary stream which feeds the combustion chamber 20 (see Figure 1).

In this embodiment, the OGV 30 is made of composite material having a fibrous reinforcement in the form of folds, embedded in a matrix. The fibrous reinforcement may include glass, carbon, aramid or ceramic fibers, etc. Furthermore, the matrix may comprise a resin, for example an epoxy, polyester, bismaleimide, or polyimide resin, etc. Preferably, the folds forming the platforms extend continuously from one platform 32 to the other platform 34, via the blade 36.

At least a first insert 100 is used for fixing the OGV 30 on the internal casing 26. The first insert 100 is here housed in the platform 32. This fixing will be detailed with reference to Figures 2 to

6. Furthermore, independently, at least one second insert 200, in this case two second inserts 200, are used for fixing the OGV 30 to the external casing 24. The second insert 200 is here housed in the platform 34. This fixing will be detailed with reference to FIGS. 7 to 10D.

Unless stated otherwise, in the following, the first and second inserts 100, 200 are described in their initial and nominal state, that is to say in their state during the initial assembly with the OGV 30 and the casing 24, 26, before possible deformation.

An embodiment of the first insert 100 is illustrated in Figures 3 to 6. The first insert comprises a socket 110 and at least one fin 120 projecting transversely from the socket 110. Here, the socket defines an axial direction X and the fin 120 protrudes in a radial or transverse direction R. More precisely, as is apparent from FIGS. 3 and 4, the fin 120 protrudes substantially along a transverse plane orthogonal to the axial direction X.

In this embodiment, the sleeve 110 is substantially symmetrical about the axis X. More specifically, the sleeve 110 comprises a base 112 (first section) from which an initial wall 114 (second second) projects axially section). Thus, the socket comprises at least two sections substantially with symmetry of revolution, namely the base 112 and the first wall 114, of different external diameters, the sections being assembled together in an axial direction of the socket 110. In the present case , the first wall 114 is tubular, more precisely cylindrical with a circular section, and has an outside diameter greater than the diameter of the base 112. The outside diameter of the first wall 114 can be equal to one and a half times the outside diameter of the base 112.

The base 112 includes an orifice, here axial, the orifice having a thread 112a. Thus, via the tapping 112a, the sleeve is configured to receive a fixing member such as a threaded rod 40 (see FIG. 5). The first wall 114 also defines an orifice whose internal diameter is greater than the diameter of the orifice of the base 112. The first wall 114 thus defines a shoulder 112b of the base 112. The shoulder 112b can act as a stop for the fixing member 40. The shoulder 112b can be provided more or less close to the free end of the first wall 114.

In this embodiment, as shown in Figure 3, the fin 120 projects from the first wall 114. Here, the fin 120 projects transversely from the socket 110 at an axial end of the socket 110 opposite the base 112. The successively increasing transverse external diameters of the base 112, of the first wall 114 and of the fin 120 define steps improving the anchoring of the first insert 100 in the platform 32, more generally in the component formed by OGV 30.

It is understood that the fin 120 is delimited in the axial direction X and extends, in this direction, over an axial thickness less than that of the sleeve 110, more precisely over an axial thickness less than that of the first wall 114.

As seen in Figure 3, the fin 120 has an axial thickness E (thickness in the axial direction X) decreasing from the sleeve 110 towards its distal end 126. In this case, the fin 120 comprises a first fin section 122, here situated level with the free end of the first wall 114 and extending transversely from the first wall 114. The fin 120 also comprises a second fin section 124, extending transversely from the first fin section 122. Each of the fin sections 122, 124 is of substantially constant axial thickness E. The axial thickness of the second fin section 124 is less than the axial thickness of the first fin section 122 which is located on the side of the sleeve 100 relative to the second fin section 124. This diagram can be repeated by recurrence in case the fin 120 comprises more than two sections. More generally, the maximum axial thickness of a fin section can be less than the minimum axial thickness of a fin section adjacent to the side of the socket 110. In the present example, the the axial thickness of the first fin section 122 is approximately twice the axial thickness of the second fin section 124.

As can be seen in Figure 4, in cross section, the fin 120 extends circumferentially between two tangents Dl, D2 of the sleeve 110, parallel to each other. The tangents D1 and D2 are therefore taken at diametrically opposite points of the socket 110, if the socket 110 is circular in cross section. The straight lines D1, D2 can be tangent to the socket 110 in its maximum diameter, here at the first wall 114.

The assembly of the first insert 100 to the OGV 30 forming a component and to the internal casing 26 forming a support is illustrated in axial section in FIG. 5. As can be seen in this figure, the insert is directly assembled to the OGV 30, as will be detailed below, and indirectly assembled to the internal casing 26, here by means of a threaded rod 40 which engages in the internal thread 112a and in a corresponding internal thread provided in the internal casing 26, for example.

Regarding the OGV 30, the first insert 100 is housed, or even embedded in the platform 32. In this case, the platform 32 comes into contact with the radially outer surface of the sleeve 110. The axially free surface of the base 112 is level with a free surface of the platform 32. Moreover, the axial dimension of the base 112 can be dimensioned more or less long so that the axially free surface of the base 112 is level with the free surface corresponding to the platform 32. Thus, when the assembly is fixed, the first insert 100 comes directly into contact with the internal casing 26, which reinforces the fixing, in particular if the first insert 100 and the internal casing 26 are made of materials similar, for example of metal or metal alloy.

A hole is made in the platform 32, in the extension of the internal diameter of the first tubular wall 114.

Furthermore, there is shown in Figure 5 sets of pleats 32a, 32b, 32c of the fiber reinforcement of the platform 32. The first insert 100 is integrated in the platform 32 by interposing the fin 120 between plies of the platform 32. In other words, the fin 120 is held, on either side in the axial direction X, by some of said folds.

In this case, the fibrous reinforcement of the platform 32 is formed by a succession of first and second plies 32a, 32b. To form an enlarged part of the platform 32, third folds 32c can be provided between the first and second folds 32a, 32b. As illustrated in FIG. 5, the fin 120 can be held on one side by a first fold 32a, on the other side by a second fold 32b. The fin 120 can be located in the extension of a third fold 32c.

As can be seen in Figures 2 and 5, the first insert 100 is provided on one side of the component, here on the upstream side of the OGV 30, and the fin 120 extends, in the OGV 30, towards an opposite side of the component, here towards the downstream side of OGV 30.

The response of the assembly thus formed to an imposed axial displacement ΔΧ of the OGV 30 relative to the internal casing 26 is shown diagrammatically in FIG. 6, in which the initial or nominal position, which is the position in FIG. 5, is shown in dotted lines. In addition, in FIG. 6, the structure of the fibrous reinforcement of the platform 32 has been simplified into a first part 32a ', on one side of the fin 120, and a second part 32b', on the other side of the fin 120 in the axial direction.

In case of displacement of the OGV 30 relative to the internal casing 26 along the X axis, in the direction of a distance of the internal casing 26 of the OGV 30, which corresponds to a relative displacement in a radial direction of the turbomachine 12, the OGV 30 composite material undergoes a local invoice at the free end 126 of the fin (zone 152), but this fracture is compensated by the plastic deformation of the fin 120 in the direction of movement 2 \ X. Indeed, the presence of the first insert 100 displaces the critical zone for fixing the zone 150, near the socket 110 and more particularly of the first wall 114, at the zone 152, at the interface between the fin 120 and the folds adjacent to the fin 220. However, in the zone 150 are exerted shear forces, to which the composite materials resist poorly, while in the zone 152 are exerted tensile-compression stresses, to which the composite materials resist more. The transfer of stresses to a more resistant zone, namely zone 152, appreciably improves the resistance of the OGV 30. The fin 120 plays the role of sacrificial part, which preferably deforms to limit the deformations of the OGV 30 proper.

An embodiment of the second insert 200 is illustrated in Figures 7 to 10D. In these figures, the elements corresponding or identical to those of the first insert 100 will be given the same reference sign, to the nearest hundreds, and will not be described again.

As illustrated in Figure 7, the second insert 200 includes all of the elements described about the first insert 100, namely a socket 210, having a base 212 and a first wall 214, and a fin 220. These elements may have all or part of the characteristics previously described.

Furthermore, the sleeve 210 further comprises a second wall 216 arranged around at least part of the first wall 214, the second wall 216 having a first end 216a connected to the first wall 214 and a second end 216b free, here on the side of base 212.

In this embodiment, the second wall 216 is at a distance from the first wall 214. More precisely, the first and second walls 214, 216 are opposite in a transverse direction R and leave between them a space.

Furthermore, the second wall 216 is tubular. In this case, the second wall 216 extends coaxially to the first wall 214, outside of the latter, around the axis X.

As shown in Figures 7 and 8, the second insert may include at least two fins, in this case two fins 220. In this embodiment, the two fins 220 are identical, also what has been said or will be said about one of the fins 220 also applies to the other, unless otherwise stated. However, in general, the fins 220 could differ from one another.

In addition, the fins 220 can be distributed circumferentially around the sleeve 210, regularly or not. In this case, the two fins 220 are diametrically opposite and both extend in the same radial direction R, in opposite directions on either side of the sleeve 210 (Figure 8). According to one example, the limit of a fin 220, in particular to distinguish it from another fin, can be defined by a change in shape of the distal end 226 of the fin 220 in the circumferential direction.

According to the example illustrated in Figure 8, in cross section, the fins 220 extend circumferentially between two lines Dl, D2 parallel to each other and defining a transverse plane, in this case the plane of Figure 8. The straight lines Dl, D2 also delimit, in this embodiment, the fins 220. The straight lines Dl, D2 can be chosen to be more distant from the axis X of the sleeve 212 than the second wall 216, so that the shape fins 220 does not interfere with the fixing of the second wall 216 on the fins 220.

Indeed, as can be seen in Figure 7, the second wall 216 protrudes from the fin 220 in the axial direction X of the socket 210. Thus, the first end 216a of the second wall 216 is connected to the first wall 214 via the fin 220, in this case via the first fin section 222.

In addition, in this case, a leave 230 is provided between the first wall 214 and the second wall 216, at the first end 216a of the second wall 216. Correspondingly but independently, leave 232 is provided between the first wall 214 and the base 212 from which the first wall 214 projects axially. Each of the leaves 230, 232 can be substantially annular. The usefulness of these leaves 230, 232 will be highlighted later.

The assembly of the second insert 200 to the OGV 30 forming the component and to the external casing 24 forming the support is illustrated in axial section in FIG. 9 and can be done, mutatis mutandis, like the assembly of the first insert 100 to the OGV 30 forming a component and the internal casing 26 forming a support.

As can be seen in Figure 9, the second insert 200 is directly assembled to the OGV 30 and indirectly assembled to the outer casing 24, here by means of a threaded rod 40 which engages in the tapping 212a and in a corresponding tapping provided in the external casing 24, for example.

In Figure 9, the structure of the fibrous reinforcement of the platform 34 has been simplified into a first part 34a ', on one side of the fin 220, and a second part 34b', on the other side of the fin 220 in the axial direction. Concerning the OGV 30, the second insert 200 is housed in the platform 34. In this case, the platform 34 comes into contact with the radially external surface of the sleeve 210, in this case in contact with the second wall 216. The second end 216b of the second wall 216, which is axially free, is level with a free surface of the platform 34. However, the base 212 extends axially beyond the second wall 216; thus, when the assembly is fixed, the second insert 200 comes directly into contact with the casing 24, which reinforces the fixing, in particular if the second insert 200 and the internal casing 24 are made of similar materials, for example metal or metal alloy.

In addition, a hole is made in the platform 34, in the extension of the internal diameter of the first tubular wall 214.

As can be seen in Figure 2, the second insert 200 is arranged in the component, here in the OGV 30, so that the transverse direction R in which the fins 220 extend corresponds to an upstream direction -OGV 30 endorsement.

The response of the assembly thus formed to an imposed displacement of the OGV 30 relative to the outer casing 26 is shown schematically in Figures 10A to 10D, each figure relating to a different type of movement. In these figures, the initial or nominal position, which is the position of Figure 9, is shown in dotted lines.

FIG. 10A deals with the case of an axial displacement ΔΧ, that is to say in a radial direction of the turbomachine, aiming to bring the outer casing 24 closer to the OGV 30. In this case, the composite material of the OGV 30 undergoes a local invoice at the free end 226 of the fin (zone 252), but this fracture is compensated by the plastic deformation of the fin 220 in the direction of movement ΔΧ. In fact, the presence of the second insert 200 displaces the critical zone for fixing the zone 254, along the second wall 216, to the zone 252, at the interface between the fin 220 and the folds adjacent to the fin 220. Now, in zone 254, shear forces are exerted, to which the composite materials resist poorly, while in zone 252, tensile-compression stresses are exerted, to which the composite materials resist more. The transfer of stresses to a more resistant zone, namely zone 252, significantly reduces the risk of rupture of the OGV 30. This mechanism also occurs in the case of an axial displacement ΔΧ in the opposite direction, such as as illustrated in Figure 10B. In this case, however, there is also a bending of the second wall 216 facilitated by the leave 230. Specifically, the second end 216b departs from the first wall 214 so as to limit the deformation of the second part 34b 'of the platform 34, which is attached to it. The second wall 216 acts as a sacrificial part, which preferably deforms to limit the deformation of the OGV itself. When the relative displacement imposed ΔΖ is a translation in an axial direction of the turbomachine 12, here in a radial direction R of the second insert 200, which is more in the transverse direction R in which the fins 220 extend, the deformation obtained can be of the type shown in FIG. 10C. As can be seen, the first wall 214 flexes in the transverse direction R, possibly to the point of assuming an S shape. This deflection is facilitated not only by the leave 230 between the first and second walls 214, 216, but also by the fillet 232 between the first wall 214 and the base 212. This deflection reduces the shear stress in an area 250, in the vicinity of the sleeve 210 and more particularly of the first wall 214. The first wall 214 acts as a sacrificial part , which preferably deforms to limit the deformation of the OGV itself.

Furthermore, as illustrated, the second wall 216 can form a stop for the deflection of the first wall 214 in the direction of the relative movement ΔΖ. The presence of such a stop is to be taken into account in the dimensioning of the insert 200, it being understood that if the platform 34 was thinner in the axial direction X, the second wall 216 could be less extended in the axial direction X and, consequently, allow a greater deflection of the first wall 214, which could even go beyond the second wall 216.

Finally, when the imposed displacement is a rotation of angle Φ in an axial plane of the second insert 200, the second insert 200 is twisted overall, so that the first wall 214 is no longer coaxial with the second wall 216 The first and second walls 214, 216 play the role of sacrificial parts, which preferably deform to limit the deformation of the OGV itself. In this case, the first wall 214 follows the rotation imposed by the outer casing 24 while the second wall 216 remains, to a certain extent, closer to its initial orientation. Such a relative offset of the first and second walls 214, 216 is facilitated by the leave 230 and limits the impact of the rotation on the first and second parts 34a ', 34b' of the platform 34.

Although an embodiment has been presented in which a first insert 100 and a second insert 200 are assembled to the OGV 30, only one of said inserts can be provided. As explained above, the presence of only one of said inserts 100, 200 already considerably strengthens the behavior of the OGV in the event of relative displacement imposed with respect to the casing 24, 26.

In fact, the use of the first and / or the second insert makes it possible to accommodate differential displacements of the order of ten millimeters without breaking, while an identical OGV without such an insert previously only withstood 'to displacements of the order of a millimeter. In the case of use as an interface between an OGV and a turbomachine casing, the first and second inserts 100, 200 may be made of metal or a metal alloy, for example made of T6A4V. More generally, the materials of the first and second inserts 100, 200 can have all or some of the following characteristics:

- Young's modulus greater than or equal to 73 gigaPascal (GPa), preferably greater than or equal to 105 GPa;

- density between 2800 and 8200 kilograms per cubic meter (kg / m ³ );

- tensile breaking stress greater than or equal to 500 megaPascal (MPa);

- specific resistance (ratio of resistance to density) greater than or equal to 0.145 MPa.m ³ / kg, preferably greater than or equal to 0.2 MPa.m ³ / kg;

- specific elongation of rupture in tension greater than or equal to 14%;

- coefficient of thermal expansion of the same order of magnitude as the coefficient of thermal expansion of the component (here of the OGV 30), that is to say multiplied or divided at most by a factor of 10, which makes it possible to reduce the clearance and thermal constraints between the insert and the component. According to one example, the coefficient of thermal expansion of the insert may be less than or equal to 10 × 10 ^-6 / ° C., the coefficient of thermal expansion of the component being generally low.

The fixing of an OGV 30, forming a component, on a casing 24, 26 of a turbomachine, forming a support, is only one example of implementation of the first and second inserts 100, 200. In particular, the role and characteristics of the support and the component can be reversed. Although the present invention has been described with reference to specific embodiments, modifications can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various illustrated / mentioned embodiments can be combined in additional embodiments. Therefore, the description and the drawings should be considered in an illustrative rather than restrictive sense.

Claims (9)

1. Insert (100) for fixing a component (30) to a support (26) of a turbomachine, the insert (100) being configured to be assembled to the component (30) and to the support (26) and comprising a bush (110) configured to receive a fixing member (40), and at least one fin (120) projecting transversely from the bush (110). 2. Insert (100) according to claim 1, wherein the sleeve (110) comprises at least two sections (112, 114) substantially symmetrical in revolution and of different external diameters, the sections (112, 114) being assembled together in an axial direction (X) of the sleeve (HO). 3. Insert (100) according to claim 1 or 2, wherein the sleeve (110) comprises a tapped internal part (112b) configured to cooperate with a threaded rod of the fixing member (40). 4. Insert (100) according to any one of claims 1 to 3, wherein the fin (120) has an axial thickness (E) decreasing from the sleeve (110) towards its distal end (126). 5. Insert (100) according to any one of claims 1 to 4, wherein, in cross section, the fin (120) extends circumferentially between two tangents (Dl, D2) of the sleeve (110) parallel between they. 6. An assembly for a turbomachine comprising a component (30) and an insert (100) according to any one of claims 1 to 5, the insert (100) being assembled to the component (30). 7. The assembly of claim 6, wherein the component (30) is of composite material having a fibrous reinforcement in the form of folds (32a, 32b, 32c), and the fin (120) is held, on both sides another in an axial direction (X), by some of said folds (32a, 32b). 8. The assembly of claim 6 or 7, wherein the insert (100) is provided on one side of the component (30) and the fin (120) extends to an opposite side of the component (30). 9. Assembly according to any one of claims 6 to 8, in which the component (30) is a turbomachine blade. 10. The assembly of claim 9, wherein the blade (30) comprises at least one platform (32) and a blade (36) extending from the platform (32), and the insert (100) is housed in the platform (32).